CN101462594B - Aerocraft capable of concealing laterally and method for manufacturing the same - Google Patents
Aerocraft capable of concealing laterally and method for manufacturing the same Download PDFInfo
- Publication number
- CN101462594B CN101462594B CN2008103053556A CN200810305355A CN101462594B CN 101462594 B CN101462594 B CN 101462594B CN 2008103053556 A CN2008103053556 A CN 2008103053556A CN 200810305355 A CN200810305355 A CN 200810305355A CN 101462594 B CN101462594 B CN 101462594B
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- aircraft
- fuselage
- fuel tank
- partition board
- tank
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Abstract
The invention discloses an aircraft capable of hiding laterally and a manufacturing method thereof. The aircraft is the prior fixed wing aircraft, rotor plane, soft wing plane or jet engine missile; when the aircraft is manufactured, two lateral surfaces of the aircraft are symmetrically provided with integral body oil tanks arranged along the length direction of an aircraft body, so that the integral body oil tanks at two sides wrap the two lateral surfaces of the aircraft totally, so fuel oil in the integral body oil tanks at the two sides can be used for attenuating radar wave emitted by a reconnaissance radar, so as to achieve lateral hiding of the aircraft. The aircraft not only has the advantage of lateral hiding, but also has the advantages of effective utilization of structure space of the aircraft body, simple structure and convenient manufacturing.
Description
Technical field
The present invention relates to aircraft of a kind of energy side invisible and preparation method thereof, belong to aircraft stealth technology field.
Background technology
At present, the fuel tank that installs on the existing aircraft fuselage generally all is arranged near the center of gravity of aircraft, this fuel tank is arranged near the aircraft center of gravity structure, must utilize high position, space, thereby the central space that takies aircraft fuselage structures is excessive, and makes the installation of aircraft finished product be subjected to limitation; Because its fuel tank is arranged in the inboard of aircraft fuselage structures, therefore existing aircraft fuel tank only is to play the effect that fuel oil stores simultaneously, and it is stealthy to help aircraft to carry out, and makes its fuel tank performance fail to make full use of.
Summary of the invention
The objective of the invention is: provide a kind of and can help the aircraft side invisible, can effectively utilize aircraft fuselage structures space and aircraft that can side invisible simple in structure, easy to make and preparation method thereof again, to overcome the deficiencies in the prior art.
The present invention is achieved in that the aircraft method for making of a kind of energy side invisible of the present invention is, when making aircraft, be symmetrical arranged the fuselage integral tank of arranging along the aircraft fuselage length direction in the two sides of aircraft, the fuselage integral tank that makes these both sides all wraps the two sides of aircraft, the radar wave that can utilize the fuel oil in the fuselage integral tank of two sides that reconnaissance radar is launched is like this decayed, thereby realizes the side invisible of aircraft.
Adopt the aircraft of a kind of energy side invisible of method making of the present invention to be: it is to improve to form on the basis of the aircraft of routine, promptly the bilateral symmetry in aircraft is provided with the reflective Partition board for fuel tank of bevelled, the common fuselage integral tank of arranging along the aircraft fuselage length direction of forming of two lateral surfaces of reflective Partition board for fuel tank and aircraft.
Be provided with the ventilation pore at the upper position place of the reflective Partition board for fuel tank that constitutes the fuselage integral tank and have the oil transportation mouth of lid, be provided with the drain oil that has seal cover cap in the lower position of reflective Partition board for fuel tank.
The number of degrees of the angle of the vertical summetry axial plane of the inclined-plane of the reflective Partition board for fuel tank of bevelled and aircraft are 10 °～40 °.
The fuselage integral tank that the common composition of two lateral surfaces of the reflective Partition board for fuel tank of bilateral symmetry setting and aircraft is arranged along the aircraft fuselage length direction in aircraft is two independently fuselage integral tanks, or be 4～20 independently fuselage integral tanks, and be symmetrically distributed in the both sides of aircraft.
Aircraft is fixed wing aircraft, cyclogyro, soft wing machine or jet engine guided missile.
The covering of the side fuselage of aircraft is the electromagnetic wave transparent material covering.
The electromagnetic wave transparent material covering is the electromagnetic wave transparent material covering of glass-felt plastic, conventional canopy material or radome material.
Reflective Partition board for fuel tank is the dividing plate made of electromagnetic wave transparent material not.
Reflective Partition board for fuel tank is the dividing plate that metallic material, metal coating material or the aluminum alloy materials of not saturating ripple made.
Owing to adopted technique scheme, the present invention to effectively utilize the aircraft fuselage structures space, and effectively utilize the radar wave that the fuel oil in the fuel tank launches reconnaissance radar and decayed, thereby realized the side invisible of aircraft well.When the radar wave of reconnaissance radar saw through the fuselage of aircraft, the fuel oil in the integral tank made the radar wave decay, thereby makes radar be difficult to detect the radar wave of reflected back; When fuel quantity in the fuel tank reduces, radar wave sees through the outside of aircraft fuselage and is mapped on the reflective Partition board for fuel tank, after the reflection of reflective Partition board for fuel tank, most of radar wave is reflected in the fuel oil and decays, other small part radar wave is reflected to the emphasis direction of non-detection, thereby makes the aircraft fuselage side invisible.So the present invention is compared with prior art, the present invention not only have can side invisible advantage, can effectively utilize aircraft fuselage structures space, advantage simple in structure, easy to make but also have.
Description of drawings
Fig. 1 is an architecture scheme drawing of the present invention;
Fig. 2 is that the A-A of Fig. 1 shows scheme drawing to cuing open.
Being labeled as of accompanying drawing: 1-aircraft, the reflective Partition board for fuel tank of 2-, 3-fuselage integral tank, the 4-pore of ventilating, 5-oil transportation mouth, 6-drain oil.
The specific embodiment
The present invention is described in further detail below in conjunction with embodiment, but not as limitation of the present invention.
Embodiments of the invention: when making aircraft by traditional mode, be symmetrical arranged the fuselage integral tank of arranging along the aircraft fuselage length direction in the two sides of aircraft according to method of the present invention simultaneously, the fuselage integral tank that makes these both sides all wraps the two sides of aircraft, the radar wave that can utilize the fuel oil in the fuselage integral tank of two sides that reconnaissance radar is launched is like this decayed, thereby realizes the side invisible of aircraft.
When specifically making the aircraft of energy side invisible of the present invention, its structural representation as depicted in figs. 1 and 2, comprise traditional aircraft 1, this aircraft 1 can be traditional fixed wing aircraft, cyclogyro, soft wing machine or jet engine guided missile, during making, bilateral symmetry in aircraft 1 is provided with the reflective Partition board for fuel tank 2 of bevelled, makes the number of degrees of angle α of the vertical summetry axial plane of the inclined-plane of the reflective Partition board for fuel tank 2 of bevelled and aircraft 1 be controlled at 10 °～40 ° scope; And the fuselage integral tank 3 that reflective Partition board for fuel tank 2 and the common composition of two lateral surfaces of aircraft 1 are arranged along aircraft 1 fuselage length direction; The common quantity of forming the fuselage integral tank of arranging along aircraft 1 fuselage length direction 3 of reflective Partition board for fuel tank 2 and two lateral surfaces of aircraft 1 can be made as two independently fuselage integral tanks, or adopt separator of battery plates to be made as 4～20 independently fuselage integral tanks, and be symmetrically distributed in the both sides of aircraft 1; Preferably the side fuselage skin of aircraft 1 is made (for example can adopt electromagnetic wave transparent materials such as glass-felt plastic, conventional canopy manufacturing materials or radome manufacturing materials to make) with electromagnetic wave transparent material during making, the manufacturing materials of reflective Partition board for fuel tank 2 is made (for example adopt metallic material, metal coating material or aluminum alloy etc. not electromagnetic wave transparent material make) with electromagnetic wave transparent material not; For easy to use, produce ventilation pore 4 at the upper position place of the reflective Partition board for fuel tank 2 that constitutes fuselage integral tank 3 and have the oil transportation mouth 5 of lid, produce the drain oil 6 that has seal cover cap in the lower position of reflective Partition board for fuel tank 2.
Claims (10)
1. the aircraft method for making of an energy side invisible, it is characterized in that: when making aircraft, be symmetrical arranged the fuselage integral tank of arranging along the aircraft fuselage length direction in the two sides of aircraft, the fuselage integral tank that makes these both sides all wraps the two sides of aircraft, the covering of the side fuselage of aircraft is the electromagnetic wave transparent material covering, the radar wave that can utilize the fuel oil in the fuselage integral tank of two sides that reconnaissance radar is launched is like this decayed, thereby realizes the side invisible of aircraft.
2. the aircraft of an energy side invisible, comprise aircraft (1), it is characterized in that, bilateral symmetry in aircraft (1) is provided with the reflective Partition board for fuel tank of bevelled (2), reflective Partition board for fuel tank (2) and the common fuselage integral tank of arranging along aircraft (1) fuselage length direction (3) of forming of two lateral surfaces of aircraft (1), the covering of the side fuselage of aircraft (1) is the electromagnetic wave transparent material covering.
3. the aircraft of energy side invisible according to claim 2, it is characterized in that: be provided with ventilation pore (4) at the upper position place of the reflective Partition board for fuel tank (2) that constitutes fuselage integral tank (3) and have the oil transportation mouth (5) of lid, be provided with the drain oil (6) that has seal cover cap in the lower position of reflective Partition board for fuel tank (2).
4. the aircraft of energy side invisible according to claim 2, it is characterized in that: the number of degrees of the angle (α) of the vertical summetry axial plane of the inclined-plane of the reflective Partition board for fuel tank of bevelled (2) and aircraft (1) are 10 °～40 °.
5. the aircraft of energy side invisible according to claim 2, it is characterized in that: the reflective Partition board for fuel tank (2) that bilateral symmetry is provided with in aircraft (1) is two independently fuselage integral tanks with the fuselage integral tank (3) that the common composition of two lateral surfaces of aircraft (1) is arranged along aircraft (1) fuselage length direction, or be 4～20 independently fuselage integral tanks, and be symmetrically distributed in the both sides of aircraft (1).
6. according to the aircraft of the described energy of arbitrary claim in the claim 2 to 5 side invisible, it is characterized in that: aircraft (1) is fixed wing aircraft, cyclogyro, soft wing machine or jet engine guided missile.
7. the aircraft of energy side invisible according to claim 2, it is characterized in that: the electromagnetic wave transparent material covering of aircraft (1) side fuselage is a glass-felt plastic.
8. the aircraft of energy side invisible according to claim 2, it is characterized in that: the electromagnetic wave transparent material covering of aircraft (1) side fuselage is the electromagnetic wave transparent material covering of conventional canopy material or radome material.
9. the aircraft of energy side invisible according to claim 2 is characterized in that: reflective Partition board for fuel tank (2) is the dividing plate that the metallic material of not saturating ripple is made.
10. the aircraft of energy side invisible according to claim 9 is characterized in that: reflective Partition board for fuel tank (2) is the dividing plate of metal coating material or aluminum alloy materials making.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008103053556A CN101462594B (en) | 2008-10-31 | 2008-10-31 | Aerocraft capable of concealing laterally and method for manufacturing the same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2008103053556A CN101462594B (en) | 2008-10-31 | 2008-10-31 | Aerocraft capable of concealing laterally and method for manufacturing the same |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101462594A CN101462594A (en) | 2009-06-24 |
| CN101462594B true CN101462594B (en) | 2010-10-06 |
Family
ID=40803430
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2008103053556A Expired - Fee Related CN101462594B (en) | 2008-10-31 | 2008-10-31 | Aerocraft capable of concealing laterally and method for manufacturing the same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101462594B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3524526A1 (en) * | 2018-02-13 | 2019-08-14 | Bell Helicopter Textron Inc. | Fuselage embedded fuel tank |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113753216B (en) * | 2021-09-19 | 2023-08-22 | 中国航空工业集团公司西安飞机设计研究所 | Ship-borne unmanned aerial vehicle platform configuration based on task modularization |
-
2008
- 2008-10-31 CN CN2008103053556A patent/CN101462594B/en not_active Expired - Fee Related
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP3524526A1 (en) * | 2018-02-13 | 2019-08-14 | Bell Helicopter Textron Inc. | Fuselage embedded fuel tank |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101462594A (en) | 2009-06-24 |
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|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20101006 Termination date: 20131031 |